| 摘要 |
<P>PROBLEM TO BE SOLVED: To provide an apparatus and a method for cooling platform regions of turbine rotor blades. <P>SOLUTION: In a turbine rotor blade having a platform at an interface between an airfoil and a root, wherein the airfoil and the root include an internal cooling passage formed therein, wherein, in operation, the internal cooling passage comprises at least a high-pressure coolant region and a low-pressure coolant region, a platform cooling apparatus includes: a platform slot extending circumferentially from a mouth formed through the positive pressure side slash face; a high-pressure connector that connects the platform slot to the high-pressure coolant region of the internal cooling passage; a low-pressure connector that connects the platform slot to the low-pressure coolant region of the internal cooling passage; and a platform cooling cartridge removably engaged within the platform slot, the platform cooling cartridge comprising one or more cartridge cooling channels. <P>COPYRIGHT: (C)2012,JPO&INPIT |
